US8505304B2 - Fuel nozzle detachable burner tube with baffle plate assembly - Google Patents
Fuel nozzle detachable burner tube with baffle plate assembly Download PDFInfo
- Publication number
- US8505304B2 US8505304B2 US12/325,559 US32555908A US8505304B2 US 8505304 B2 US8505304 B2 US 8505304B2 US 32555908 A US32555908 A US 32555908A US 8505304 B2 US8505304 B2 US 8505304B2
- Authority
- US
- United States
- Prior art keywords
- burner tube
- fuel nozzle
- assembly
- baffle plate
- swirler assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 82
- 238000002485 combustion reaction Methods 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims description 40
- 230000008878 coupling Effects 0.000 claims description 14
- 238000010168 coupling process Methods 0.000 claims description 14
- 238000005859 coupling reaction Methods 0.000 claims description 14
- 230000000284 resting effect Effects 0.000 claims description 9
- 239000012530 fluid Substances 0.000 claims description 5
- 239000007789 gas Substances 0.000 description 17
- 230000000712 assembly Effects 0.000 description 10
- 238000000429 assembly Methods 0.000 description 10
- 230000007246 mechanism Effects 0.000 description 8
- 230000005465 channeling Effects 0.000 description 7
- 239000000203 mixture Substances 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
- 230000004323 axial length Effects 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 229910001220 stainless steel Inorganic materials 0.000 description 3
- 239000010935 stainless steel Substances 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000001939 inductive effect Effects 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 229910000856 hastalloy Inorganic materials 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00017—Assembling combustion chamber liners or subparts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Definitions
- the present invention relates generally to gas turbine engines and, more particularly, to a detachable burner tube for use with a gas turbine engine.
- a burner tube assembly is the outermost component of at least some known fuel nozzle assemblies and is designed to protect a plurality of internal components within the fuel nozzle assembly while channeling the air/fuel mixture through the fuel nozzle assembly.
- a plurality of components are welded together along a plurality of seams.
- inlet air flow is determined by the burner tube assembly at the time of assembly and is generally inflexible to any subsequent changes. More specifically, to implement a design change to the air flow generally requires replacement of the entire fuel nozzle assembly. In addition, during assembly, any damage to the burner tube assembly itself may require a repair of the entire fuel nozzle assembly. The assembly process is further complicated by the burner tube assembly, which limits access to the internal components of the fuel nozzle assembly, thus making such components difficult to inspect and service.
- the burner tube assembly is designed such that the air flow becomes substantially uniform as it flows downstream.
- the seams created between the components coupled together may create flow anomalies, such as recirculation zones, that may adversely affect the operation of the fuel nozzle assembly.
- each joint requires special attention to prevent flame holding issues wherein trapped fuel and air may automatically ignite.
- some known burner tube assemblies are not coupled to a support flange, and, in such tubes, a first natural bending frequency of the fuel nozzle assembly may be low enough to be excited by rotor speed multiples, thus increasing a risk of part failure due to vibration.
- a method for assembling a fuel nozzle for use with a combustion chamber defined within a gas turbine engine includes providing a swirler assembly, providing a burner tube, and coupling the burner tube to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.
- a fuel nozzle configured to channel fluid toward a combustion chamber defined within a gas turbine.
- the fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.
- a gas turbine engine in yet another aspect, includes a combustion chamber and a fuel nozzle configured to channel fluid toward the combustion chamber.
- the fuel nozzle includes a swirler assembly, a burner tube, and a support flange, wherein the burner tube is coupled to the support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.
- FIG. 1 is a schematic illustration of an exemplary gas turbine engine
- FIG. 2 is a cross-sectional schematic illustration of an exemplary combustor that may be used with the gas turbine engine shown in FIG. 1 ;
- FIG. 3 is a cross-sectional schematic illustration of a known fuel nozzle assembly
- FIG. 4 is a cross-sectional schematic illustration of an exemplary fuel nozzle assembly that may be used with the combustor shown in FIG. 2 that includes a detachable burner tube;
- FIG. 5 is a partially broken away perspective of another embodiment of a fuel nozzle assembly that may be used with the combustor shown in FIG. 2 .
- the exemplary methods and systems described herein overcome the disadvantages of known fuel nozzle assemblies and provide a fuel nozzle assembly that is simpler to assemble, disassemble, and service in comparison to known fuel nozzle assemblies.
- axial and axially refer to directions and orientations extending substantially parallel to a center longitudinal axis of a centerbody of a burner tube assembly.
- radial refers to directions and orientations extending substantially perpendicular to the center longitudinal axis of the centerbody.
- upstream and downstream refer to directions and orientations relative to an axial flow direction with respect to the center longitudinal axis of the centerbody.
- FIG. 1 is a schematic illustration of an exemplary gas turbine engine.
- Gas turbine engine 100 includes a compressor 102 and a combustor 104 , which includes a fuel nozzle assembly 106 .
- Gas turbine engine 100 also includes a turbine 108 and a common compressor/turbine shaft 110 .
- gas turbine engine 100 is a PG9371 9FBA Heavy Duty Gas Turbine Engine, commercially available from General Electric Company, Greenville, S.C.
- the present invention is not limited to any one particular engine and may be used in connection with other gas turbine engines.
- combustor 104 During operation, air flows through compressor 102 and compressed air is supplied to combustor 104 and, more specifically, to fuel nozzle assembly 106 .
- Fuel is channeled to a combustion region defined within combustor 104 , wherein the fuel is mixed with the compressed air and the mixture is ignited.
- Combustion gases are generated and channeled to turbine 108 , wherein gas stream thermal energy is converted to mechanical rotational energy.
- Turbine 108 is rotatably coupled to, and drives, shaft 110 .
- FIG. 2 is a cross-sectional schematic view of combustor 104 .
- Combustor 104 is coupled in flow communication with compressor 102 and turbine 108 .
- Compressor 102 includes a diffuser 112 and a compressor discharge plenum 114 that are coupled in flow communication with each other.
- Combustor 104 includes an end cover 120 that provides structural support to a plurality of fuel nozzle assemblies 122 . End cover 120 is coupled to combustor casing 124 with retention hardware (not shown in FIG. 2 ).
- a combustor liner 126 is positioned radially inward from combustor casing 124 such that combustor liner 126 defines a combustion chamber 128 within combustor 104 .
- An annular combustion chamber cooling passage 129 is defined between combustor casing 124 and combustor liner 126 .
- a transition piece 130 is coupled to combustor chamber 128 to facilitate channeling combustion gases generated in combustion chamber 128 downstream towards turbine nozzle 132 .
- transition piece 130 includes a plurality of openings 134 formed in an outer wall 136 .
- Transition piece 130 also includes an annular passage 138 that is defined between an inner wall 140 and outer wall 136 .
- Inner wall 140 defines a guide cavity 142 .
- fuel nozzle assembly 122 is coupled to end cover 120 via a fuel nozzle flange (not numbered).
- turbine 108 drives compressor 102 via shaft 110 (shown in FIG. 1 ).
- compressor 102 rotates, compressed air is discharged into diffuser 112 as the associated arrows illustrate.
- the majority of air discharged from compressor 102 is channeled through compressor discharge plenum 114 towards combustor 104 , and the remaining compressed air is channeled for use in cooling engine components.
- pressurized compressed air within discharge plenum 114 is channeled into transition piece 130 via outer wall openings 134 and into annular passage 138 .
- Air is then channeled from annular passage 138 through annular combustion chamber cooling passage 129 and to fuel nozzle assemblies 122 .
- Fuel and air are mixed, and the mixture is ignited within combustion chamber 128 .
- Combustor casing 124 facilitates shielding combustion chamber 128 and its associated combustion processes from the outside environment such as, for example, surrounding turbine components. Combustion gases generated are channeled from combustion chamber 128 through guide cavity 142 and towards turbine nozzle 132 .
- FIG. 3 is a cross-sectional schematic illustration of a known fuel nozzle assembly 300 .
- An outermost component of known fuel nozzle assembly 300 is an outer tube 310 .
- Outer tube 310 protects a plurality of internal components such as a swirler assembly 320 and a stem 330 while channeling fluids through known fuel nozzle assembly 300 .
- outer tube 310 is assembled from a plurality of components including an upper tube 350 , also known as an inlet flow conditioner (IFC), that is welded to an upstream side of a swirler shroud 370 and a lower tube 360 , also known as a burner tube, that is welded to a downstream side of swirler shroud 370 .
- IFC inlet flow conditioner
- outer tube 310 is assembled by tightly rolling at least one piece of sheet metal circumferentially about swirler assembly 320 . More specifically, outer tube 310 fully circumscribes and is coupled to swirler assembly 320 via welding. Outer tube 310 includes a plurality of perforated openings 380 defined therein. Perforated openings 380 enable air to enter outer tube 310 at its base end proximate to a flange 340 .
- FIG. 4 is a cross-sectional schematic illustration of an exemplary fuel nozzle assembly 400 that includes a detachable burner tube 410 , a stem 420 , and a swirler assembly 430 .
- detachable burner tube 410 is the radially outermost component of fuel nozzle assembly 400 and radially encases fuel nozzle assembly 400 .
- detachable burner tube 410 includes a base region 412 and a side wall 414 .
- swirler assembly 430 is fabricated from a first material that has a first coefficient of thermal expansion (CTE), and detachable burner tube 410 is fabricated from a second material that has a second CTE different from the first CTE.
- second material is capable of withstanding higher temperatures than the first material due to its proximity to combustor 104 (shown in FIG. 1 ).
- use of the second material enables detachable burner tube 410 to maintain its shape and resist corrosion and oxidation at material temperatures above approximately 1200° F.
- the respective materials facilitate ensuring that an inner surface defining an inner diameter of detachable burner tube 410 is positioned against an outer surface defining an outer diameter of swirler assembly 430 .
- the respective materials facilitate creating a tight seal, at operating temperature, between detachable burner tube 410 and swirler assembly 430 such that the inner diameter of detachable burner tube 410 and the outer diameter of swirler assembly 430 are in structural contact without inducing excessive strain to detachable burner tube 410 or swirler assembly 430 during fuel nozzle operation.
- detachable burner tube 410 and swirler assembly 430 define a joint that provides a structural stiffness of fuel nozzle assembly 400 that is configured to transmit loads during operation.
- the respective materials also facilitate axially sliding, at resting or room temperature, detachable burner tube 410 about stem 420 towards and away from a flange 440 .
- a gap is defined between the inner surface defining the inner diameter of detachable burner tube 410 and the outer surface defining the outer diameter of swirler assembly 430 at both resting and operating temperatures. In such an embodiment, the gap does not substantially affect the operation of fuel nozzle assembly 400 .
- a heat assisted process is used to expand detachable burner tube 410 enough to couple detachable burner tube 410 about stem 420 and swirler assembly 430 .
- detachable burner tube 410 is capable of securely coupling to and easily uncoupling from flange 440 via a coupling mechanism 450 .
- Coupling mechanism 450 may include any apparatus capable of coupling and decoupling detachable burner tube 410 to and from flange 440 including, but not limited to, a bolted joint and/or a cam-locking mechanism.
- detachable burner tube 410 When detachable burner tube 410 is coupled to flange 440 , detachable burner tube 410 provides axial support to fuel nozzle assembly 400 . More specifically, flange 440 and coupling mechanism 450 are configured to provide vibration robustness to detachable burner tube 410 .
- a plurality of air passage openings 460 are formed in side wall 414 and circumscribe base region 412 of detachable burner tube 410 proximate to flange 440 and are sized and configured to facilitate access to coupling mechanism 450 .
- Coupling mechanism 450 enables detachable burner tube 410 to be easily interchanged, which facilitates improved serviceability. For example, rather than replacing an entire fuel nozzle assembly 400 when a detachable burner tube 410 is damaged or worn, a detachable burner tube 410 to be replaced can be easily uncoupled and replaced by a new detachable burner tube 410 .
- Coupling mechanism 450 also facilitates accessing internal components within fuel nozzle assembly 400 such as stem 420 and swirler assembly 430 for service, repair, and inspection by uncoupling detachable burner tube 410 and recoupling detachable burner tube 410 as necessary.
- interchanging detachable burner tube 410 facilitates changing an air flow design of fuel nozzle assembly 400 by replacing a detachable burner tube 410 with any one of a plurality of detachable burner tubes 410 of various air flow designs.
- detachable burner tube 410 channels an air flow within fuel nozzle assembly 400 . More specifically, air enters fuel nozzle assembly 400 via air passage openings 460 and is channeled through detachable burner tube 410 to swirler assembly 430 . In the exemplary embodiment, detachable burner tube 410 facilitates channeling air flow such that the air flow is substantially uniform upstream of swirler assembly 430 . More specifically, an axial length 470 , between air passage openings 460 and swirler assembly 430 , and a radial length 480 , between stem 420 and detachable burner tube 410 , facilitate channeling a desired air flow. In one embodiment, lengths 470 and 480 facilitate eliminating a need for air guide vanes within swirler assembly 430 .
- FIG. 5 is a partially broken away perspective of fuel nozzle assembly 500 , which is an alternate embodiment of fuel nozzle assembly 400 .
- fuel nozzle assembly 500 includes many of the same components as fuel nozzle assembly 400 as shown in FIG. 4 , including stem 420 , swirler assembly 430 , flange 440 , coupling mechanism 450 , and plurality of air passage openings 460 .
- fuel nozzle assembly 500 includes a detachable burner tube 510 with an upper tube 520 proximate to flange 440 and a lower tube 530 proximate to combustor 104 (shown in FIG.
- baffle plate assembly 550 includes a baffle plate 560 and a bell-shaped air guide vane 590 coupled to stem 420 .
- baffle plate assembly 550 is positioned radially inward of plurality of perforated openings 540 that are circumferentially spaced about detachable burner tube 510 .
- detachable burner tube 510 includes upper and lower tubes 520 and 530 for cost efficiency purposes. More specifically, lower tube 530 is fabricated from a material that is capable of withstanding high temperatures due to its proximity to combustor 104 (shown in FIG. 1 ).
- upper tube 520 is fabricated from 410 stainless steel, which has a CTE of 6.4e-6 in/in/° F.
- lower tube 530 is fabricated from Hastalloy X, which has a CTE of 8.03e-6 in/in/° F.
- use of the material enables lower tube 530 to maintain its shape and resist corrosion and oxidation at material temperatures above approximately 1200° F.
- detachable burner tube is fabricated from one material that is capable of withstanding high temperatures due to its proximity to combustor 104 (shown in FIG. 1 ).
- swirler assembly 430 is fabricated from a first material that has a first CTE
- upper tube 520 is fabricated from a second material that has a second CTE, different from the first CTE.
- the respective materials of swirler assembly 430 and detachable burner tube 510 facilitate ensuring that the inner surface defining the inner diameter of detachable burner tube 510 is positioned against the outer surface defining the outer diameter of swirler assembly 430 .
- the respective materials of swirler assembly 430 and upper tube 520 facilitate creating a tight seal, at operating temperature, between upper tube 520 and swirler assembly 430 without inducing excessive strain to upper tube 520 or swirler assembly 430 during fuel nozzle operation.
- upper tube 520 and swirler assembly 430 define a joint that provides a structural stiffness of fuel nozzle assembly 500 that is configured to transmit loads during operation.
- the respective materials of swirler assembly 430 and upper tube 520 also facilitate axially sliding, at resting or room temperature, detachable burner tube 510 about stem 420 towards and away from a flange 440 .
- swirler assembly 430 is fabricated from 347 stainless steel, which has a CTE of 9.81e-6 in/in/° F.
- upper tube 520 is fabricated from 410 stainless steel, which has a CTE of 6.4e-6 in/in/° F.
- the respective materials of swirler assembly 430 and lower tube 530 are selected to facilitate ensuring that the inner surface defining the inner diameter of lower tube 530 is positioned against the outer surface defining the outer diameter of swirler assembly 430 as described above for upper tube 520 .
- baffle plate assembly 550 facilitates channeling a shorter and broader air flow within fuel nozzle assembly 500 than fuel nozzle assembly 400 . More specifically, baffle plate assembly 550 enables a configuration of burner tube 510 wherein an axial length 570 is shorter than axial length 470 (shown in FIG. 4 ) and a radial length 580 is longer than radial length 480 (shown in FIG. 4 ).
- the detachable burner tube described herein facilitates the operation of a gas turbine engine. More specifically, the detachable burner tube described herein simplifies assembly and disassembly of the fuel nozzle and provides vibration robustness, continuity of flow path, and service flexibility. Practice of the methods, apparatus, or systems described or illustrated herein is neither limited to a detachable burner tube nor to gas turbine engines generally. Rather, the methods, apparatus, and systems described or illustrated herein may be utilized independently and separately from other components and/or steps described herein.
Abstract
Description
Claims (11)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/325,559 US8505304B2 (en) | 2008-12-01 | 2008-12-01 | Fuel nozzle detachable burner tube with baffle plate assembly |
DE102009044708A DE102009044708A1 (en) | 2008-12-01 | 2009-11-30 | Removable burner tube of a fuel nozzle |
JP2009270905A JP5451344B2 (en) | 2008-12-01 | 2009-11-30 | Removable burner tube for fuel nozzle |
CN200910253371.XA CN101806460B (en) | 2008-12-01 | 2009-12-01 | Fuel nozzle detachable burner tube |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/325,559 US8505304B2 (en) | 2008-12-01 | 2008-12-01 | Fuel nozzle detachable burner tube with baffle plate assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
US20100132364A1 US20100132364A1 (en) | 2010-06-03 |
US8505304B2 true US8505304B2 (en) | 2013-08-13 |
Family
ID=42221553
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/325,559 Expired - Fee Related US8505304B2 (en) | 2008-12-01 | 2008-12-01 | Fuel nozzle detachable burner tube with baffle plate assembly |
Country Status (4)
Country | Link |
---|---|
US (1) | US8505304B2 (en) |
JP (1) | JP5451344B2 (en) |
CN (1) | CN101806460B (en) |
DE (1) | DE102009044708A1 (en) |
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US20140260299A1 (en) * | 2013-03-12 | 2014-09-18 | General Electric Company | Fuel-air mixing system for gas turbine system |
US20140338339A1 (en) * | 2013-03-12 | 2014-11-20 | General Electric Company | System and method having multi-tube fuel nozzle with multiple fuel injectors |
US20140338340A1 (en) * | 2013-03-12 | 2014-11-20 | General Electric Company | System and method for tube level air flow conditioning |
US9347668B2 (en) | 2013-03-12 | 2016-05-24 | General Electric Company | End cover configuration and assembly |
US9366439B2 (en) | 2013-03-12 | 2016-06-14 | General Electric Company | Combustor end cover with fuel plenums |
US9528444B2 (en) | 2013-03-12 | 2016-12-27 | General Electric Company | System having multi-tube fuel nozzle with floating arrangement of mixing tubes |
US9534787B2 (en) | 2013-03-12 | 2017-01-03 | General Electric Company | Micromixing cap assembly |
US9651259B2 (en) | 2013-03-12 | 2017-05-16 | General Electric Company | Multi-injector micromixing system |
US9671112B2 (en) | 2013-03-12 | 2017-06-06 | General Electric Company | Air diffuser for a head end of a combustor |
US9765973B2 (en) | 2013-03-12 | 2017-09-19 | General Electric Company | System and method for tube level air flow conditioning |
US10982857B2 (en) * | 2018-02-23 | 2021-04-20 | DOOSAN Heavy Industries Construction Co., LTD | Nozzle for combustors, combustor, and gas turbine including the same |
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US8522555B2 (en) * | 2009-05-20 | 2013-09-03 | General Electric Company | Multi-premixer fuel nozzle support system |
US8371123B2 (en) | 2009-10-28 | 2013-02-12 | General Electric Company | Apparatus for conditioning airflow through a nozzle |
US8418469B2 (en) * | 2010-09-27 | 2013-04-16 | General Electric Company | Fuel nozzle assembly for gas turbine system |
US20120305670A1 (en) * | 2011-06-06 | 2012-12-06 | General Electric Company | System for conditioning flow through a combustor |
US9366445B2 (en) | 2012-04-05 | 2016-06-14 | General Electric Company | System and method for supporting fuel nozzles inside a combustor |
EP2685054B1 (en) * | 2012-07-09 | 2020-11-25 | ABB Schweiz AG | Diffuser of an exhaust gas turbine |
US9016064B2 (en) | 2012-07-10 | 2015-04-28 | General Electric Company | Combustor |
US9046038B2 (en) | 2012-08-31 | 2015-06-02 | General Electric Company | Combustor |
US9546789B2 (en) * | 2013-03-15 | 2017-01-17 | General Electric Company | System having a multi-tube fuel nozzle |
JP6206648B2 (en) * | 2013-07-08 | 2017-10-04 | 三菱日立パワーシステムズ株式会社 | Chip holder, combustor nozzle including the same, combustor including the combustor nozzle, and method for manufacturing the combustor nozzle |
US20150013342A1 (en) * | 2013-07-12 | 2015-01-15 | Solar Turbines Inc. | Air flow conditioner for fuel injector of gas turbine engine |
CN103697499B (en) * | 2014-01-15 | 2016-08-17 | 大连海事大学 | A kind of variable swirling number cyclone |
US10955141B2 (en) * | 2017-06-19 | 2021-03-23 | General Electric Company | Dual-fuel fuel nozzle with gas and liquid fuel capability |
KR102340397B1 (en) * | 2020-05-07 | 2021-12-15 | 두산중공업 주식회사 | Combustor, and gas turbine including the same |
KR102583227B1 (en) * | 2022-01-26 | 2023-09-25 | 두산에너빌리티 주식회사 | Combustor replaceable for each unit cluster and gas turbine including the same |
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2008
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-
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- 2009-11-30 DE DE102009044708A patent/DE102009044708A1/en not_active Withdrawn
- 2009-12-01 CN CN200910253371.XA patent/CN101806460B/en not_active Expired - Fee Related
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Also Published As
Publication number | Publication date |
---|---|
JP5451344B2 (en) | 2014-03-26 |
CN101806460B (en) | 2014-11-26 |
JP2010127613A (en) | 2010-06-10 |
CN101806460A (en) | 2010-08-18 |
US20100132364A1 (en) | 2010-06-03 |
DE102009044708A1 (en) | 2010-09-09 |
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